加力燃烧室NOx排放生成规律试验分析

实现航空发动机大推力通常采用加力燃烧室设计,燃烧室进气温度升高会同步导致排放尾气中NO_x浓度提高.采用典型加力燃烧室主稳定器的V型结构试验件,测试加力燃烧前后(进口600 ℃,出口600~1 200 ℃)燃烧室排放断面的NO_x浓度分布,通过相同流场4种试验工况的NO_x生成浓度组分和氧含量变化分析,验证了加力燃烧室NO_x生成以热力型NO为主的"高温、富氧、贫油"燃烧特性.结果表明加力燃烧室燃烧过程中消耗的氧含量大多贡献于CO₂增量,在800~1 000 ℃燃气排放温度范围内,不完全燃烧产物CO对NO的热力生成有明显抑制作用.

Experimental analysis on NOx generation and emission distribution off aviation afterburners

An afterburners was designed to get aviation engine extra thrust,but higher inlet temperature will generate higher NOx emission.One V style structure test facilities was adopted as an afterburners flow fields stabilizer,the section concentration of different NOx and O2 emission from the afterburners were analyzed in condition of inlet T 600 ℃ to outlet T 600~1 200 ℃,the test was fulfilled at 4 experimental conditions of same flux and flow fields.The results show that the chamber combustion is of "higher temperature,rich oxygen,poor fuel" characteristics,most Oxygen consumption in an afterburner chamber is contributed to generate CO2 and in the emission temperature scope of 800~1 200 ℃,the NO thermal generation is restrained and affected by incomplete combustion product CO evidently.